Method for manufacturing composite fiber preform for disc brakes

ABSTRACT

An example method includes combining an interlayer and a carbon fiber fabric, wherein the interlayer comprises a highly oriented milled carbon fiber ply comprising a plurality of out-of-plane carbon fibers. The method further includes winding the interlayer and the carbon fiber fabric around a core to form a composite fiber preform comprising a plurality of layers defining an annulus extending along a central axis. The method further includes densifying the composite fiber preform.

TECHNICAL FIELD

The disclosure relates to the manufacture of carbon-carbon compositematerials, such as the manufacture of aircraft brake pads or discs madeof carbon-carbon composite materials.

BACKGROUND

Carbon-carbon composite materials are composite materials that include acarbon matrix and carbon fiber reinforcements. Carbon-carbon (C-C)composite components can be used in many high temperature applications.For example, the aerospace industry employs C-C composite components asfriction materials for commercial and military aircraft, such asfriction brake materials.

Some carbon-carbon composites, such as some carbon-carbon compositebrake discs that are used in the aerospace industry, may be manufacturedfrom porous preforms that include layers of carbon fiber, which may bedensified using one or more of several processes, including chemicalvapor deposition/chemical vapor infiltration (CVD/CVI), vacuum/pressureinfiltration (VPI), or resin transfer molding (RTM), to infiltrate theporous preform with carbon.

SUMMARY

In some examples, this disclosure describes a method including combiningan interlayer and a carbon fiber fabric, wherein the interlayercomprises a highly oriented milled carbon fiber ply comprising aplurality of out-of-plane carbon fibers; winding the interlayer and thecarbon fiber fabric around a core to form a composite fiber preformcomprising a plurality of layers defining an annulus extending along acentral axis; and densifying the composite fiber preform.

In some examples, this disclosure describes a composite fiber preformincluding a carbon fiber fabric; and an interlayer comprising a highlyoriented milled carbon fiber ply comprising a plurality of out-of-planecarbon fibers, wherein the interlayer and the carbon fiber fabric arewound around a core to form a composite fiber preform comprising aplurality of layers defining an annulus extending along a central axis,wherein the interlayer and the carbon fiber fabric are at leastpartially densified.

In some examples, this disclosure describes a system including a fabricsource including a carbon fiber fabric; an interlayer source comprisingan interlayer comprising a plurality of out-of-plane carbon fibers; anda winding apparatus configured to wind the carbon fiber fabric and theinterlayer around a core to form a composite fiber preform and definingan annulus extending along a central longitudinal axis, the compositefiber preform including: a plurality carbon fiber fabric layersextending in an axial direction parallel with the longitudinal axis anda circumferential direction perpendicular to both the radial and axialdirections, wherein each of the plurality of carbon fiber fabric layerscomprises a plurality of elongate carbon fibers oriented substantiallyparallel with the axial and circumferential directions; and a pluralityinterlayers extending in an axial direction parallel with thelongitudinal axis and a circumferential direction perpendicular to boththe radial and axial directions, wherein the plurality of out-of-planecarbon fibers of interlayers are oriented substantially parallel withthe radial direction and configured to mechanically bind one or moreadjacent carbon fiber fabric layers.

In some examples, this disclosure describes a method including: formingan interlayer on a carbon fiber fabric to form a composite fiber fabric,wherein the interlayer comprises a binder; winding the composite fiberfabric and interlayer around a core to form a composite fiber preformcomprising a plurality of layers defining an annulus extending along acentral axis; and densifying the composite fiber preform.

In another example, this disclosure describes a composite fiber preformincluding: a plurality carbon fiber fabric layers wrappedcircumferentially about a longitudinal axis and extending in an axialdirection parallel with the longitudinal axis, wherein each of theplurality of carbon fiber fabric layers comprises a plurality ofelongate carbon fibers; and a plurality interlayers wrappedcircumferentially about the longitudinal axis and extending in the axialdirection, wherein each of the plurality of interlayers are disposedbetween successive layers of the plurality of carbon fabric layers andcomprise a binder configured to mechanically bind one or more adjacentcarbon fiber fabric layers.

In another example, this disclosure describes a system including: afabric source including a carbon fiber fabric; an interlayer source; anda winding apparatus configured to wind the carbon fiber fabric and theinterlayer around a core to form a composite fiber preform and definingan annulus extending along a central longitudinal axis, the fiberpreform including: a plurality carbon fiber fabric layers extending inan axial direction parallel with the longitudinal axis and acircumferential direction perpendicular to both the radial and axialdirections, wherein each of the plurality of carbon fiber fabric layerscomprises a plurality of elongate carbon fibers; and a pluralityinterlayers extending in an axial direction parallel with thelongitudinal axis and a circumferential direction perpendicular to boththe radial and axial directions, wherein the interlayer comprises abinder configured to mechanically bind one or more adjacent carbon fiberfabric layers.

The details of one or more examples of the disclosure are set forth inthe accompanying drawings and the description below. Other features,objects, and advantages of the disclosure will be apparent from thedescription and drawings, and from the claims.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a conceptual diagram illustrating an example wheel and brakeassembly that may include one or more of brake discs formed inaccordance with the techniques and structural features of thisdisclosure.

FIG. 2 is a schematic perspective view of an example stator brake discthat defines both an inner diameter (ID) and an outer diameter (OD).

FIG. 3A is a schematic perspective view of an example composite fiberpreform that may be used to manufacture the composite friction materialsdescribed herein.

FIG. 3B is a partial cross-section of a portion of the composite fiberpreform as indicated in FIG. 3A.

FIG. 3C is a cross-section of the composite fiber preform that may beused to manufacture the composite friction materials described herein.

FIG. 4A is a conceptual diagram illustrating an example system formanufacturing the composite fiber preform of FIG. 3A.

FIG. 4B is a conceptual diagram illustrating another example system formanufacturing the composite fiber preform of FIG. 3A.

FIG. 5A is a cross-section of an example interlayer that may be used tomanufacture the composite friction materials described herein.

FIG. 5B is a cross-section of another example interlayer that may beused to manufacture the composite friction materials described herein.

FIG. 5C is a cross-section of another example interlayer that may beused to manufacture the composite friction materials described herein.

FIGS. 6A and 6B are heat maps illustrating example peak temperatureduring braking procedures of an example friction composite materialmanufactured using the techniques described herein and an examplenon-woven friction composite material.

FIG. 7 is a graph of peak antioxidant temperature versus time for anexample friction composite material manufactured using the techniquesdescribed herein and an example non-woven friction composite material.

FIG. 8 is a flow diagram illustrating an example technique ofmanufacturing a composite fiber preform.

FIG. 9 is a flow diagram illustrating another example technique ofmanufacturing a composite fiber preform.

DETAILED DESCRIPTION

The present disclosure describes, in some examples, a composite frictionmaterial and methods of manufacturing a composite friction material thatmay be used, for example, to form a carbon-carbon composite brake discor other carbon-carbon composite brake pad. Methods of manufacturing thecarbon-carbon composite friction material may include winding a carbonfiber-based fabric and an interlayer onto a core or a mandrel to form acomposite fiber preform. The layers of the composite fiber preform maybe arranged in concentric layers, e.g., wound into an annulus and/or acylinder extending along a central longitudinal axis. The carbon fibers(e.g., alternatively referred to as just “fibers” throughout) within thelayers may be orientated predominately in the axial and circumferentialdirections of the wound cylinder.

Composite friction materials, such as composite aircraft brake pads, maywear during braking operations. In the example of aircraft brakes,increasing the usable life of the brake pads may be accomplished byincreasing a wear pin length, decreasing a wear rate of the frictionmaterial, or both. Often, the wear pin is already at a maximum length.Hence, decreasing wear rate of a brake pad may be beneficial. Fiberorientation in composite brake pads may affect wear rates and thermalconductivity. In some examples, preforms used to form composite aircraftbrake pads in the form of annular brake discs may include alternatinglayers of radial and chordal (e.g., circumferential) fiber fabricsegments, such that a majority of the fibers lie in the radial andcircumferential directions of the brake disc, e.g., substantially withina plane perpendicular to the axial direction of the annular disc.Needling of the fiber segments of the preform may be used to introduce arelatively low percentage of fibers in the axial direction. Typically,needling or tufting is used to provide mechanical stability in anaxially compacted state for handling in subsequent steps and to provideadequate fiber volume fraction.

Orienting a relatively large amount of fibers of a composite frictionmaterial in an axial direction relative to the longitudinal axis of anannulus defined by the disc brake, for example, normal to a frictionsurface, may decrease wear rate, increase thermal conductivity (in theaxial direction), and increase useable life of the composite frictionmaterial. Additionally or alternatively, axial orientation of the fibersmay improve thermal conductivity from the friction surface to heatsinks,such as a backing plate. For example, by better conducting heat, theaxially oriented fibers may lower peak temperatures and/or reduce timeat temperature exposure during operation, which may increase a useablelife of the friction material and/or an antioxidant coating on thefriction material. Additionally or alternatively, axial orientation offibers may improve mid-disc densification via chemical vaporinfiltration or chemical vapor deposition (CVI/CVD) process by providingpreferentially-oriented fibers, which may reduce density gradients,potentially increase bulk density leading to lower bulk temperatures,and/or potentially reduce the number of CVI/CVD cycles to achieverequired density.

According to techniques of the current disclosure, an interlayer may bewound with a carbon fiber fabric around a core, e.g., via a windingapparatus and/or onto a mandrel, to form a preform. As will bedescribed, the use of the interlayer may provide for attachment and/oradhesion between successive windings and/or layers in the radialdirection within the preform, e.g., in order to provide a desiredmechanical stability of the wound fabric. In some examples, interlayermay be selected to provide a desired radially oriented fiber content toprovide a desired interlayer attachment and/or mechanical stability ofthe wound fabric, e.g., which may eliminate or reduce the need forneedling/tufting of the preform. In other examples, the interlayer maybe selected to provide a desired binding and/or adhesion force toprovide the desired mechanical stability of the wound fabric. The carbonfabric may be selected to consolidate during winding, e.g., bycontrolling tension, to increase the fiber volume fraction within thepreform. Additionally, the carbon fiber fabric may comprise fibers thatare relatively more evenly dispersed, e.g., relative to conventionalcarbon fiber fabrics bundled in tows. The relatively more even dispersalof fibers may improve infiltration/densification of the preform insubsequent processing steps.

In example methods and systems disclosed herein, a composite fiberpreform may be formed by combining an interlayer and a carbon fiberfabric. The interlayer may include a highly oriented milled carbon fiberply that includes a plurality of out-of-plane (or radial when wound)carbon fibers. The interlayer and the carbon fiber fabric may be woundaround a core to form the composite fiber preform including a pluralityof layers defining an annulus extending along a central axis. Thecomposite fiber preform may then be densified.

In some examples, the carbon ply may be deposited onto the carbon fiberfabric from a peel ply. For example, the carbon ply may be disposed on apeel-ply prior to winding, and during winding the peel-ply may be mergedwith the carbon fiber fabric to deposit the highly oriented milledcarbon fiber on a surface of the carbon fiber fabric. Subsequently, thepeel-ply backing may be removed, e.g., prior to winding of the carbonply and carbon fiber fabric. In some examples, the carbon fiber fabricmay comprise a carbon felt, as further described below.

In another example, the interlayer may include a binder rather than acarbon fiber ply. The interlayer, e.g., binder, may be formed on thecarbon fiber fabric to form a composite fiber fabric. The compositefiber fabric, e.g., carbon fiber fabric and binder, may be wound arounda core to form the composite fiber preform including a plurality oflayers defining an annulus extending along a central axis. The compositefiber preform may then by densified.

In some examples, a plurality of nanoparticles may be combined with, orincluded with, the binder. The plurality of nanoparticles may be carbonnanotubes, carbon nanofibers, graphene nanoplatelets, and the like. Thebinder may include any suitable binder configured to bind and/or causesuccessive windings of the composite fiber fabric to adhere. In someexamples, the binder may be a resin, a thermoset resin, a phenolicresin, and the like. In some examples, the binder may be configured toinclude and/or mix with the nanoparticles. The binder, optionallyincluding the plurality of nanoparticles, may be deposited on the carbonfiber fabric as a dry coating, a dry powder, a solution, or any suitabledepositing method.

FIG. 1 is a conceptual diagram illustrating an example wheel and brakeassembly 10 that may include one or more of brake pads or discs formedin accordance with the techniques and structural features of thisdisclosure. For ease of description, examples of the disclosure will bedescribed primarily with regard to composite friction materials in theform of brake discs that may be employed in aircraft brake assembliessuch as that shown in FIG. 1 . However, the techniques of thisdisclosure may be used to form composite friction materials other thanaircraft brake discs. For example, the composite friction materials maybe used in other types of vehicles or friction material applicationsfrom which they may benefit, e.g., improved wear rate and/or improvedthermal conductivity.

In the example of FIG. 1 , wheel and brake assembly 10 includes a wheel12, an actuator assembly 14, a brake stack 16, and an axle 18. Wheel 12includes wheel hub 20, wheel outrigger flange 22, bead seats 24A and24B, lug bolt 26, and lug nut 28. Actuator assembly 14 includes actuatorhousing 30, actuator housing bolt 32, and piston 34. Brake stack 16includes alternating rotor brake discs 36 and stator brake discs 38;rotor brake discs 36 are configured to move relative to stator brakediscs 38. Rotor brake discs 36 are mounted to wheel 12, and inparticular wheel hub 20, by beam keys 40. Stator brake discs 38 aremounted to axle 18, and in particular torque tube 42, by splines 44.Wheel and brake assembly 10 may support any variety of private,commercial, or military aircraft or other type of vehicle.

Wheel and brake assembly 10 includes wheel 12, which in the example ofFIG. 1 is defined by a wheel hub 20 and a wheel outrigger flange 22.Wheel outrigger flange 22 may be mechanically affixed to wheel hub 20 bylug bolts 26 and lug nuts 28. Wheel 12 defines bead seals 24A and 24B.During assembly, an inflatable tire (not shown) may be placed over wheelhub 20 and secured on an opposite side by wheel outrigger flange 22.Thereafter, lug nuts 28 can be tightened on lug bolts 26, and theinflatable tire can be inflated with bead seals 24A and 24B providing ahermetic seal for the inflatable tire.

Wheel and brake assembly 10 may be mounted to a vehicle via torque tube42 and axle 18. In the example of FIG. 1 , torque tube 42 is affixed toaxle 18 by a plurality of bolts 46. Torque tube 42 supports actuatorassembly 14 and stator brake discs 38. Axle 18 may be mounted on a strutof a landing gear (not shown) or other suitable component of the vehicleto connect wheel and brake assembly 10 to the vehicle.

During operation of the vehicle, braking may be necessary from time totime, such as during landing and taxiing procedures of an aircraft.Wheel and brake assembly 10 is configured to provide a braking functionto the vehicle via actuator assembly 14 and brake stack 16. Actuatorassembly 14 includes actuator housing 30 and piston 34. Actuatorassembly 14 may include different types of actuators such as one or moreof, e.g., an electrical-mechanical actuator, a hydraulic actuator, apneumatic actuator, or the like. During operation, a piston 34 mayextend away from actuator housing 30 to axially compress brake stack 16against compression point 48 for braking.

Brake stack 16 includes alternating rotor brake discs 36 and statorbrake discs 38. Rotor brake discs 36 are mounted to wheel hub 20 forcommon rotation by beam keys 40. Stator brake discs 38 are mounted totorque tube 42 by splines 44. In the example of FIG. 1 , brake stack 16includes four rotors and five stators. However, a different number ofrotors and/or stators may be included in brake stack 16 in otherexamples.

Rotor brake discs 36 and stator brake discs 38 may provide opposingfriction surfaces for braking an aircraft. As kinetic energy of a movingaircraft is transferred into thermal energy in brake stack 16,temperatures may rapidly increase in brake stack 16. As such, rotorbrake discs 36 and stator brake discs 38 that form brake stack 16 mayinclude robust, thermally stable materials capable of operating at veryhigh temperatures.

Rotor brake discs 36 and stator brake discs 38 may be examples ofcarbon-carbon composite brake pads. In one example, rotor brake discs 36and/or stator brake discs 38 are formed as a carbon-carbon (C-C)composite in the form of an annulus that defines a set of opposing wearsurfaces. The C-C composite may be fabricated using any suitablemanufacturing technique or combination of techniques including, forexample, vacuum pressure infiltration (VPI), resin transfer molding(RTM), chemical vapor infiltration (CVI), chemical vapor deposition(CVD), additive manufacturing, mechanical machining, ablationtechniques, or the like using the fiber preforms describe herein as thestarting substrate.

In some examples, rotor brake discs 36 and stator brake discs 38 may bemounted in wheel and brake assembly 10 by beam keys 40 and splines 44,respectively. In some examples, beam keys 40 may be circumferentiallyspaced about an inner portion of wheel hub 20. Beam keys 40 may, forexample, be shaped with opposing ends (e.g., opposite sides of arectangular) and may have one end mechanically affixed to an innerportion of wheel hub 20 and an opposite end mechanically affixed to anouter portion of wheel hub 20. Beam keys 40 may be integrally formedwith wheel hub 20 or may be separate from and mechanically affixed towheel hub 20, e.g., to provide a thermal barrier between rotor brakediscs 36 and wheel hub 20. In some examples, wheel and brake assembly 10may include a heat shield (not shown) that extends out radially andoutwardly surrounds brake stack 16, e.g., to limit thermal transferbetween brake stack 16 and wheel 12.

In some examples, splines 44 may be circumferentially spaced about anouter portion of torque tube 42. As such, stator brake discs 38 mayinclude a plurality of radially inwardly disposed lug notches along aninner diameter of the brake disc configured to engage with splines 44.Similarly, rotor brake discs 36 may include a plurality of radiallyinwardly disposed lug notches along an outer diameter of the brake discconfigured to engage with beam keys 40. As such rotor brake discs 36will rotate with the motion of the wheel while stator brake discs 38remain stationary allowing the friction surfaces of an adjacent statorbrake disc 38 and rotor brake disc 36 to engage with one another todeaccelerate the rotation of wheel 12.

As will be described further below, one or more of brake discs 36, 38may be a carbon-carbon composite material formed using one or more ofthe techniques described herein. In some examples, brake discs 36, 38may be formed via sectioning a composite carbon fiber preform in a rollformat, e.g., after further processing such as densification,carbonization, and/or other processing steps. For example, the compositecarbon fiber preform may be formed via winding a carbon fiber fabricsuch that in-plane fibers of the carbon fiber fabric are re-oriented inan axial-circumferential plane of brake discs 36, 38 after sectioning.

FIG. 2 is a schematic perspective view of an example stator brake disc38 that defines both an inner diameter (ID) and an outer diameter (OD).Stator brake disc 38 may be an example of the similarly numbered brakediscs 38 of FIG. 1 . Stator brake disc 38 includes opposing frictionsurfaces 70 positioned on opposite sides of the annulus. An inner radialsection 74 along inner diameter ID of stator brake disc 38 includes aplurality of lug notches 72 cut into stator brake disc 38. Lug notches72 are configured to engage and interlink with splines 44 of wheel andbrake assembly 10. For a rotor brake disc 36, lug notches 72 would occuralong an outer radial section 76 along outer diameter OD of the annulus.Lug notches 72 of a rotor brake disc 36 would be configured to engageand interlink with beam keys 40.

During a braking procedure, splines 44 and beam keys 40 may engage withthe respective lug notches 72 of rotor and stator brakes discs 36 and 38generating heat between adjacent friction surfaces 70 and transferring alarge amount of torque into the brake discs. Heat generated during thebraking procedure may be conducted through fibers of brake disc 38. Insome examples, an orientation of the underlying fiber architecture ofthe C-C composite may affect heat conduction. For example, heatconduction may be greater parallel to the longitudinal length of thefibers, compared to a direction transverse to the longitudinal length ofthe fibers. In some examples, fibers of the C-C composite that areoriented in an axial direction (relative to the circumferentialdirection or the radial direction), may conduct more heat betweenfriction surfaces 70 and/or toward the core (in the axial direction) ofbrake disc 38 (e.g., away from friction surface 70 in the axialdirection) than fibers oriented in the circumferential direction or theradial direction. Transferring heat between adjacent friction surfacesand/or toward the core of brake disc 38 may reduce localized build-up ofheat, which may otherwise increase wear, damage protective coatings,and/or reduce the useable life of brake disc 38. In this way, fiberarchitectures of brake discs 36 and 38 may be selected to decrease wearrate, increase thermal conductivity in the axial direction, and increaseuseable life of the composite friction material.

Additionally, the torque forces created during the braking procedure maybe transferred into the underlying fiber architecture of the C-Ccomposite. In some examples, if the fibers of the C-C composite areoriented in a radial direction, the resultant forces may be exerted in adirection generally transverse to the longitudinal length of the fibers.In contrast, if the fibers are oriented in a circumferential direction(e.g., aligned perpendicular to the radial direction), the resultantforces may be exerted in a direction generally along the longitudinallength of the fibers. Fiber architectures of brake discs 36 and 38 maybe selected to provide a desired torque transfer near lug notches 72.

According to some techniques described herein, stator brake disc 38 maybe formed via sectioning a composite carbon fiber preform in a rollformat, e.g., after further processing such as densification,carbonization, and/or other processing steps. For example, the compositecarbon fiber preform may be formed via winding a carbon fiber fabricsuch that in-plane fibers of the carbon fiber fabric are in anaxial-circumferential plane of stator brake disc 38 after sectioning.

FIG. 3A is a schematic perspective view of an example composite fiberpreform 100 that may be formed according to the techniques disclosedherein and may be used to manufacture the composite friction materialsdescribed herein (e.g., rotor or stator brake discs 36 and 38 of FIGS. 1and 2 ). FIG. 3B is a partial cross-section of composite fiber preform100 (the cross-section is indicated in FIG. 3A). FIG. 3C is across-section of composite fiber preform 100 as viewed along its axis,e.g., central longitudinal axis 110, including compaction layer 312 andcore 310. Composite fiber preform 100 defines an annulus extending alonga central longitudinal axis 110 (e.g., extending parallel to thez-axis). Composite fiber preform 100 includes a plurality of superposedfibrous layers 102 (“layers 102”) and interlayers (“layers 103”). Layers102 and interlayers 103 extend in an axial direction “A” and acircumferential direction “C” relative to the longitudinal axis. Asillustrated in FIG. 3B, layers 102 include layers 102A-102E wound aroundlongitudinal axis 110, and interlayers 103 include interlayers 103A-103Dwound around longitudinal axis 110 and disposed between respectivelayers 102 as shown. For example, layers 102 and interlayers 103 may becombined and continuously wound around longitudinal axis 110, e.g., in acontinuous spiral. In other examples, layers 102 and interlayers 103 mayinclude discrete rings. As described below, layers 102 may includecarbon fibers or carbon precursor fibers and layers 102 may be referredto as carbon fiber fabric layers.

In some examples, layers 102 may include a continuous fiber fabric, suchas a uniaxial fabric or a biaxial fabric. For example, each of layer 102may include a plurality of continuous axial fibers 104 (“axial fibers104”) extending substantially in the axial direction and a plurality ofcontinuous circumferential fibers 106 (“circumferential fibers 106”)extending substantially in the circumferential direction. As usedherein, extending substantially in the axial, circumferential, or radialdirections may refer to extending in the respective direction relativeto longitudinal axis 110 (e.g., relative to the annulus) to the extentallowable given composite fiber manufacturing tolerances, e.g.,deviations not exceeding +/−5 degrees, such as +/−2 degrees. Continuousfibers may include infinitely long fibers that are continuous at leastacross the entirety of layers 102. In some examples, a continuous fiberfabric may include a woven fabric having any suitable weave pattern. Insome examples, layers 102 may include alternating layers of a continuousfiber fabric and a nonwoven fabric.

In some examples, interlayers 103 may introduce a plurality of thirdfibers 108 (“radial fibers 108”) extending substantially in the radialdirection “R” into composite fiber preform 100. Radial fibers 108 maymechanically bind layers 102 together. For example, radial fibers 108may secure at least one layer of layers 102 to one or more adjacentlayers of layers 102. In this way, radial fibers 108 may increase aninterlaminar shear strength of composite fiber preform 100 and/or brakedisc 38 formed from composite fiber preform 100. Additionally oralternatively, the interlayer and resulting radial fibers 108 maypartially compress layers 102, e.g., via tensioning the interlayers 103during winding, to form a more compacted composite fiber preform 100compared to a preform including a similar number of layers 102 that havenot been compressed. The compaction may increase the fiber volumefraction carbon fibers of preform 100.

While some of the figures described herein show a relatively smallnumber of layers to form the respective fiber preforms, the preforms(e.g., composite fiber preform 100) produced as a result of thetechniques describe herein may include any suitable number of layers 102and interlayers 103 to produce the desired outer diameter OD of theresultant preform. For example, each layer 102 and/or interlayer 103 mayhave a thickness as measured in the radial direction of about 1millimeter (mm) to about 2 mm. In some examples, each layer 102 and/orinterlayer 103 may have a different thickness than about 1 to about 2mm, and/or may have thicknesses that are different from each other.Composite fiber preform 100, once completed, may be in the shape of anannulus defining an outer preform diameter (OD) and inner preformdiameter (ID). In some examples, the outer preform diameter (OD) ofcomposite fiber preform 100 may be about 14.5 inches (e.g., about 37 cm)to about 25 inches (e.g., about 64 cm) and the inner preform diameter(ID) of composite fiber preform 100 may be about 4.5 inches (e.g., about12 cm) to about 15 inches (e.g., about 38 cm). Hence, in some examples,fiber preform may include between about 30 layers and about 520 layers.In other examples, fiber preform may include less than 30 layers or morethan 520 layers.

In some examples, after forming preform 100, e.g., before or after anyone of pyrolysis (or other carbonization), or densification of perform100, perform 100 may be sectioned (e.g., cut) along thecircumferential/radial plane (e.g., parallel to the xy-plane) to form abrake disc (e.g., brake disc 38). In some examples, a total thickness(T) of each sectioned portion of composite fiber preform 100 may beabout 1 inch to about 3 inches (e.g., about 2.54 cm to about 7.62 cm).

In some examples, composite fiber preform 100 may be constructed withlug notches 72 (not shown in FIG. 3A) formed into either the outerdiameter (OD) or inner diameter (ID) depending on whether compositefiber preform 100 is intended to be formed as a rotor brake disc 36 orstator brake disc 38 respectively. In some examples, a region of preform100 at lug notches 72, for example, with about 3 inches (e.g., about7.62 cm) of lug notches 72 may include more radial fibers 108 comparedto other regions of fiber perform 100. A greater concentration of radialfibers 108 near lug notches 72 may improve torque transfer strength atlug notches 72. In some examples, lug notches may be formed togetherwith fiber perform 100, may be cut into composite fiber preform 100after the respective layers 102 have all been wound, or may beintroduced after composite fiber preform 100 has undergone some or allof the subsequent carbonization (e.g., pyrolyzation) and densificationprocedures to convert composite fiber preform 100 into a C-C composite.

In some examples, the fiber preform may be in the shape of an annulus(e.g., disc-shaped) that defines both an inner diameter ID and an outerdiameter OD. A cross section of the fiber preform annulus may be dividedinto an inner radial section, a central radial section, and an outerradial section. For example, layers 102A and 102B may define the innerradial section, layers 102C-102E may define the central radial section,and layers 102G and 102F may define the outer radial section. In otherexamples, the inner radial section, the central radial section, and theouter radial section may include any suitable number of layers. In otherexamples, the inner radial section, the central radial section, and theouter radial section may each include between about 5% to about 90% of atotal width W of the annulus.

In some examples, each of the inner radial section and outer radialsection may include a greater percentage of radial extending fibers(relative to axial or circumferential extending fibers), compared to apercentage of radial extending fibers in the central radial section. Insome examples, a percentage of radial extending fibers may be selectedbased on the location of a lug region within the final fiber preform(e.g., region configured to receive lug notches that interlock with thesplines or beam keys of a wheel and brake assembly).

Axial fibers 104, circumferential fibers 106, and radial fibers 108 mayinclude carbon fibers, fibers configured to subsequently carbonize(e.g., pyrolyze) into carbon fibers (hereinafter “carbon-precursorfibers”), or combinations thereof. Carbon-precursor fibers may include,for example, polyacrylonitrile (PAN) fibers, oxidized polyacrylonitrile(O-PAN) fibers, rayon fibers, pitch fibers, or the like.

In some examples, axial fibers 104 and/or circumferential fibers 106,may be in the form of tows (e.g., bundles of individual fibers linearlyaligned) of continuous filaments. Each tow may include hundreds toseveral thousand of individual fibers unidirectionally aligned to form asingle tow. In such examples, layers 102 may include a fabric having aplurality of unidirectionally aligned tows within the segment with eachtow including a plurality of fibers.

In some examples, layers 102 may be in the form of a fabric. Forexample, layers 102 may be in the form of a woven fabric, a knittedfabric, a unidirectional stitched fabric, or the like.

In some examples, layers 102 may be in the form of a felt, e.g., acarbon felt. The carbon felt may be selected to consolidate duringwinding, e.g., by controlling tension. Additionally, the carbon felt maycomprise carbon fibers that may be more evenly dispersed than a fibertow, which may improve infiltration/densification of the preform insubsequent processing steps. In some examples, the felt (e.g., layers102) may be a non-woven carbon felt and may comprise carded,cross-lapped, and needled O-PAN staple fibers that may initially berelatively short before carding, cross-lapping, and needling. The feltmay also be heat treated, which may convert at least a portion of theO-PAN fibers to carbon. In some examples, layers 102 may include aduplex fabric that includes a plurality of unidirectionally alignedaxial fibers 104 and/or circumferential fibers 106 (e.g., aligned tows)that have been combined with a plurality of web fibers (not shown). Theweb fibers may include chopped, discontinuous, or staple fibers havingan unspecified alignment that are relatively short in comparison toaxial fibers 104 and/or circumferential fibers 106 that, when combinedwith axial fibers 104 and/or circumferential fibers 106 in a duplexfabric, become intertwined with aligned axial fibers 104 and/orcircumferential fibers 106 to impart integrity to each layer of layers102. The web fibers may define a random fiber orientation relative toeach other and to aligned axial fibers 104 and/or circumferential fibers106.

In some examples, the formation of a duplex fabric may be accomplishedby combining one or more layers of aligned tow fibers (e.g., axialfibers 104 and/or circumferential fibers 106) with one or more layers ofweb fibers that are subsequently needle-punched into the layer of towfibers to form duplex fabric. For example, a layer of web fibers may beformed by cross-lapping a carded web to achieve a desired areal weightand then needle-punching the layer to form the web layer. Additionally,or alternatively, the web layer may be formed by air-laying the webfibers on top of a layer of the unidirectionally aligned fibers. Thelayer of unidirectionally aligned fibers may be formed by spreadinglarge continuous tows using a creel, to form a sheet of the desiredareal weight with fibers being aligned in the same direction. Both theweb layer and the layer of unidirectionally aligned fibers may beneedle-punched together to force the relatively short web fibers tobecome intertwined with unidirectionally aligned fibers to form theduplex fabric (e.g., layers 102).

Additionally, or alternatively layers 102 may be formed as a duplexfabric by initially incorporating web fibers within tows ofunidirectionally aligned fibers. A layer of the described tows may beformed by spreading large the tows using a creel, to form a sheet of thedesired areal weight. The layer may then be needle-punched to force therelatively short web fibers to become intertwined with unidirectionallyaligned fibers thereby forming the duplex fabric.

As a result of needling process in either of the above examples, the webfibers become intertwined with the aligned fibers and help bind alignedfibers together allowing layers 102 to be efficiently handled withouthaving aligned fibers separate or fall apart with subsequent processing.The resultant duplex fabric (e.g., layers 102) may be more durable,retain its shape better, and be overall easier to further manufacturecompared to a layer of only unidirectionally aligned fibers. Othertechniques may also be used to form layers 102 as a duplex fabric thatincludes both unidirectionally aligned fibers and web fibers which maybe known to those skilled in the art. In all the examples describedherein, layers 102 and the fabric segments used to from the fiberpreforms described herein may be composed of one or more layers of aduplex fabric.

As a result of winding process in either of the above examples, theradial fibers 108 become intertwined with the aligned axial fibers 104and/or circumferential fibers 106 and help bind aligned fibers togetherallowing combined layers 102 and interlayers 103 to be efficientlyhandled without having aligned fibers separate or fall apart withsubsequent processing. The resultant carbon fiber preform 100 may bemore durable, retain its shape better, and be overall easier to furthermanufacture compared to layers of carbon fiber fabric, carbon felt,duplex fabric, or the like, including only in-plane fibers.

Both the radial fibers 108 and in-plane fibers 104, 106 may be formed ofthe same carbon fiber or carbon fiber precursor materials, may be formedof different carbon fiber or carbon fiber precursor materials, or may beformed of different combinations of carbon fiber and/or carbon fiberprecursor materials. In some examples, layers 102 may be formed to havean areal weight of about 500 grams per square meter (g/m²) to about 2500g/m² such as, about 597 g/m²to about 1346 g/m².

In some examples, composite fiber preform 100 may optionally be wrappedwith a compaction layer 312 around the outer diameter of composite fiberpreform 100 and may include a core 310, as illustrated in FIG. 3C.Compaction layer 312 may be configured to maintain a compaction of thecomposite fiber preform 100, and may comprise a filament wound carbontow. In some examples, each of layers 102 and 103 may providecompaction, and may be referred to as a compaction layer. For example,the compaction force of each layer 102 and/or 103 may be caused, andproportional to, tension on the layer as it is wound about core 310 or amandrel. In some examples, the fiber volume of each layer may also beaffected, and/or controlled, by the tension on layers 102 and/or 103 asthey are wound. For example, tension may need to decrease as a functionof radius of composite fiber preform 100 to maintain a constant fibervolume. Conversely, a constant tension on layers 102 and/or 103 as afunction of radius of composite fiber preform 100 may result in a fibervolume gradient as a function of radius of composite fiber preform 100,e.g., from the inner diameter to the outer diameter of composite fiberpreform 100. In other words, the fiber volume of composite fiber preform100 as a function of radius of composite fiber preform 100 may becontrolled by controlling the tension of layers 102 and/or 103 as theyare wound.

In some examples, core 310 may support the inner diameter of compositefiber preform 100 and may comprise a filament wound carbon tow. In someexamples, core 310 may be removable from composite fiber preform 312, ormay be integral to, included with, and/or a part of carbon fiber preform100. In some examples, core 312 may be configured to couple to amandrel, e.g., so as to wind carbon fiber preform 100. In some examples,composite fiber preform 100 may be thermally cycled to rigidize at leastone of core 310, the composite fiber preform 100, or compaction layer312.

FIG. 4A is a conceptual diagram illustrating an example system 400 formanufacturing composite fiber preform 100. System 400 includes a fabricsource 402 and interlayer source 404. In the example shown, fabricsource 402 includes a length of carbon fiber fabric 412 wound into aroll, and interlayer source 404 includes a length of interlayer 414wound into a roll. System 400 is configured to wind and/or combinecarbon fiber fabric 412 and interlayer 414 into composite fiber preform100.

Fiber preform is configured to wind carbon fabric 414 and interlayer 412into composite fiber preform 100. Composite fiber preform 100 may bewound about a core 410 which may extend along central longitudinal axisin the axial direction. In some examples, composite fiber preform 100may be coupled to a motor (not shown). The motor may be configured tocontrollably core 410 to wind carbon fiber fabric 412 from fabric source402 and interlayer 414 from interlayer source 404 around core 410 toform composite fiber preform 100. In some example, the motor may includea variable speed motor communicatively coupled to a controller (notshown). The controller may be configured to control a speed of rotationof core 410.

In some examples, core 410 may include a material that can be heated tobetween about 1900° C. and about 2500° C. For example, core 410 mayinclude a graphite mandrel. In some examples, core 410 may include agraphite ring removably attached to a metal rod. In some examples, core410 may be removable from composite fiber preform 100, e.g., after fiberpreform is wound and/or after one or more subsequent densificationand/or consolidation processing steps.

Fabric source 402 may be a roll of carbon fiber fabric 412 that is woundaround a core 420. Fabric source 402 may be a roll of carbon fiberfabric 412 comprising a material including in-plane carbon fibers, e.g.,an in-plane carbon fiber fabric, a roll of fiber tow fabric, a carbonfelt and/or a carbon-based felt, and the like. Carbon fiber fabric 412may be an example of layers 102 described above. Core 420 may be coupledto a tensioner (not shown), for example, a tension bar, one or more niprollers, an electric motor or a braking system configured to provide aselected tension on carbon fiber fabric 412 as core 410 is rotated towind carbon fiber fabric 412 from fabric source 402 onto composite fiberpreform 100. System 400 may additionally or alternatively include one ormore tensioning rollers 416 (e.g., nip rollers, idlers, adjustableand/or translatable idlers, web steering rollers and the like)configured to provide a selected tension on the carbon fiber fabric 412as core 410 is rotated to wind carbon fiber fabric 412 onto compositefiber preform 100. In some examples, the selected tension may affect thedensity of a fiber perform 100, e.g., an in-plane fiber volume and/ordensity (e.g., axial fibers 104 and/or circumferential fibers 106)relative to a total volume and/or density of composite fiber preform100. For example, a greater tension during winding may result in adenser fiber perform 100 compared to a lesser tension. In some examples,a tension may be selected to result in a selected in-plane fiber volumeand/or density relative to a total volume and/or density of compositefiber preform 100. For example, a tension may be selected to result in apercent in-plane fiber volume relative to a total volume of compositefiber preform 100 between about 15% to about 50%, such as about 22% toabout 25%.

Interlayer source 404 may be a length of interlayer 414 that is woundaround a core 430. Interlayer 414 may include a plurality of radialfibers 408 deposited on a carrier 418 that is wound around a core 430 toform interlayer source 404. Interlayer 414 may be an example ofinterlayers 103 and radial fibers 408 may be substantially similar toradial fibers 108 described above. Interlayer 414 may include radialfibers 408 that include a plurality of out-of-plane and/or “radially”oriented carbon fibers, e.g., oriented parallel with the “thickness,” orshortest dimension, of interlayer 414. In some examples, interlayer 414may be a highly oriented milled carbon fiber ply disposed on a carrier418, e.g., a removable backing, a peel ply, or any other suitablecarrier material. For example, interlayer 414 may comprise radial fiber408 that are highly oriented, e.g., having their long dimension along adirection that is substantially perpendicular to a surface of thecarrier material. In some examples, substantially all (approximately100%) of radial fibers 408 have their long dimension substantiallyperpendicular to the surface of the carrier material, e.g., asillustrated in FIG. 5C below. In some examples, substantially all(approximately 100%) of radial fibers 408 have their long dimensionoriented greater than or equal to 45 degrees from the surface of thecarrier material (e.g., radial fibers 408 are substantially all orientedwithin (or equal to) +/−45 degrees from the surface normal of thecarrier material, as illustrated in FIG. 5B below). In some examples,the radial thickness of interlayer 414 may be defined by the averagelength of radial fibers 408. In some examples, the average length ofradial fiber 408 is about 150 microns. In some examples, interlayer 414may include radial fibers 408 that may have different properties or mayhave been processed differently than, for example, the in-plane carbonfibers of carbon fiber fabric 412. For example, carbon fiber fabric 412may be heat treated without stretch control, whereas the highly orientedmilled carbon fiber ply may be heat treated with stretch control.

Core 430 may be coupled to a tensioner (not shown), for example, anelectric motor or a braking system configured to provide a selectedtension on radial fiber source 404 as core 410 is rotated to wind radialfibers 408 onto composite fiber preform 100. System 400 may additionallyor alternatively include one or more tensioning rollers 416 (e.g., niprollers, idlers, adjustable and/or translatable idlers, web steeringrollers and the like) configured to provide a selected tension on radialfibers 408 (or a web material or removable backing material onto whichradial fibers 408 are disposed) as core 410 is rotated to wind radialfibers 408 onto composite fiber preform 100. In some examples, theselected tension may affect a density of fiber perform 100, e.g., afiber volume and/or density relative to a total volume and/or density ofcomposite fiber preform 100. For example, a greater tension duringwinding may result in a denser fiber perform 100 and an increasedamount/length of radial fibers 408 extending into the adjacent carbonfiber fabric 412 layers of preform 100 compared to a lesser tension. Insome examples, a tension may be selected to result in a selected radialfibers 408 volume and/or density relative to a total volume and/ordensity of composite fiber preform 100.

In some examples, combination of carbon fiber fabric 412 and interlayer414 by winding onto preform 100 may introduce a plurality of radialfibers 408 extending in the radial direction of preform 100 andextending into one or more layers of carbon fiber fabric 412, e.g.,extending into adjacent in-plane fiber fabric layers 412. In someexamples, the tension of one or both of carbon fiber fabric 412 andinterlayer 414 may be controlled to provide a selected amount of radialfibers 408 in selected regions of composite fiber preform 100. Forexample, during winding of the inner radial section of preform 100, afirst tension of carbon fiber fabric 412 and a first tension ofinterlayer 414 may provide a greater amount of radial fibers 408, or agreater amount of the length of radial fibers 408 extending within oneor more carbon fiber fabric 412 layer, relative to a central radialsection (e.g., central with respect to width W of FIG. 3A) wound with asecond tension of carbon fiber fabric 412 and/or a second tension ofinterlayer 414 (e.g., each of the tensions may be varied independentlyor in any combination to increase or decrease the amount of radialfibers 408 and/or the amount of length that radial fibers 408 extendwithin adjacent layers). Similarly, during winding of the outer radialsection of preform 100, a third tension of carbon fiber fabric 412and/or a third tension of interlayer 414 may provide a greater amount ofradial fibers 408, or a greater amount of the length of radial fibers408 extending within one or more adjacent layers. In this way, compositefiber preform 100 may be formed to have a selected amount (e.g.,percentage) of radially extending fibers 408 relative to axial fibers104 and/or circumferential fibers 106, or a selected amount of thelength of radial fibers 408 extending within one or more carbon fiberfabric 412 layers.

FIG. 4B is a conceptual diagram illustrating an example system 450 formanufacturing composite fiber preform 100. System 450 includes a fabricsource 452 and a coater 454. System 450 is configured to form interlayer464 on carbon fiber fabric 462 to form composite fiber fabric 470 andwind the composite fiber fabric 470 to form composite fiber preform 100.

Composite fiber preform 100 may be wound about a core 410 which mayextend along central longitudinal axis in the axial direction. In someexamples, composite fiber preform 100 may be coupled to a motor (notshown). The motor may be configured to controllably wind fabric fromfabric source 452 around core 410 to form composite fiber preform 100.In some example, the motor may include a variable speed motorcommunicatively coupled to a controller (not shown). The controller maybe configured to control a speed of rotation of core 410.

In some examples, core 410 may include a material that can be heated tobetween about 1900° C. and about 2500° C., as described above. Forexample, core 410 may include a graphite mandrel. In some examples, core410 may include a graphite ring removably attached to a metal rod.

In some examples, fabric source 452 may be a roll of carbon fiber fabric462 that is wound around a core 420. Carbon fiber fabric 462 maycomprise a material including in-plane carbon fibers, e.g., a roll offiber tow fabric, a carbon felt, a carbon knit fabric, apolyacrylonitrile (PAN) fiber, an oxidized PAN fiber such as PANOX®, andthe like. Carbon fiber fabric 462 may be an example of layers 102described above. Core 420 may be coupled to a tensioner (not shown), forexample, a tension bar, one or more nip rollers, an electric motor or abraking system configured to provide a selected tension on source fabric452 as core 410 is rotated to wind fabric from fabric source 452 ontocomposite fiber preform 100. System 450 may additionally oralternatively include one or more tensioning rollers 466 (e.g., niprollers, idlers, adjustable and/or translatable idlers, web steeringrollers and the like) configured to provide a selected tension on thecarbon fiber fabric 462 as core 410 is rotated to wind carbon fiberfabric 462 onto composite fiber preform 100. In some examples, theselected tension may affect a density of fiber perform 100, e.g., afiber volume relative to a total volume of composite fiber preform 100.For example, a greater tension during winding may result in a denserfiber perform 100 compared to a lesser tension. In some examples, atension may be selected to result in a selected fiber volume relative toa total volume of composite fiber preform 100. For example, a tensionmay be selected to result in a percent fiber volume relative to a totalvolume of composite fiber preform 100 between about 1% to about 50%,such as about 15% to about 25%.

Coater 454 may be configured to coat or otherwise deposit a materialthat forms interlayer 464 on a surface of carbon fiber fabric 412.Interlayer 464 may comprise a binder 459, and optionally a plurality ofnanoparticles 458 mixed within binder 459. In some examples, coater 454may be a hopper configured to deposit the binder 459 onto a surface ofcarbon fiber fabric 462. For example, the binder 459 may be a dry powderof binder material, and a hopper may be configured to deposit the drybinder onto carbon fiber fabric 462. In some example, binder 459 mayinclude nanoparticles 458, e.g., pre-mixed with binder 459. In otherexamples, the hopper may be configured to receive and mix nanoparticles458 with binder 459 and deposit the binder 459 with nanoparticles 458onto the carbon fiber fabric 462. In still other examples, coater 454may comprise more than one hopper, and a first hopper may be configuredto deposit binder 459 or nanoparticles 458 onto the carbon fiber fabric462, and a second downstream, e.g., in the direction of movement ofcarbon fiber fabric 462 during winding, hopper may be configured todeposit the other of nanoparticles 458 or binder 459 onto the carbonfiber fabric to mix and form interlayer 464. In some examples, coater454 may be configured to deposit a binder solution onto a surface ofcarbon fiber fabric 462. For example, the binder 459 may be mixed with asolvent, such as an organic solvent, methyl ethyl ketone (MEK), acetoneor any suitable solvent, to form a binder solution, and a coater 454 maybe configured to coat and/or spray a surface of carbon fiber fabric 462with the binder solution. The binder solution may be further mixed withnanoparticles 458 prior to coating onto the carbon fiber fabric 462. Insome examples, whether deposited as a dry binder or coated as a bindersolution, binder 459 may comprise a weight percent (wt %) of the drycarbon fiber fabric 462 between about 10 wt % to about 30 wt %. In someexamples, when added to the dry binder or the binder solution,nanoparticles 458 may comprise a weight percent (wt %) of the binder 459between about 2 wt % to about 10 wt %.

Binder 459 may comprise a resin, a thermoset resin, a phenolic resin, anadhesive or the like. Binder 459 may have a curing temperature range ofabout 100 degrees Celsius) to about 280 degrees Celsius and a highcarbon yield during carbonization. In some examples, binder 459 may bean phenolic resin, for example, Durite and Bakelite or Borden resin fromHexion Inc. of Columbus, Ohio.

In some examples, whether deposited as a dry binder or coated as abinder solution, and whether containing nanoparticles 458 or not, binder459 and carbon fiber fabric 462 may be compressed prior to winding toform composite fiber preform 100. For example, nip rollers 466 may beconfigured to compress binder 459 and carbon fiber fabric 462, and/orpress roller 468 may be configured to compress binder 459 and carbonfiber fabric 462. The binder solution may be dried, e.g., before orafter winding, and binder 459, whether in dry form or as a solution andwhether containing nanoparticles 458 or not, may be cured after winding.For example, composite fiber preform 100 may be heated to cure binder459.

In some examples, binder 459, whether containing nanoparticles 458 ornot, may be configured to bind and/or adhere adjacent and/or successivecarbon fiber fabric layers, e.g., of carbon fiber fabric 462. In someexamples, binder 459 may be configured to improve a property ofcomposite fiber preform 100, e.g., to improve shear strength, tensilestrength, and/or any other suitable mechanical property of carbon fiberpreform 100, successive layers of carbon fiber preform 100, and/or brakediscs formed from carbon fiber preform 100. Binder 459 may have anysuitable thickness. In some examples, binder 459 may have a thicknessranging from about 0.05 millimeters (mm) to about 0.6 mm.

Nanoparticles 458 may be single-walled or multi-walled carbon nanotubes,carbon nanofibers, a graphene nanoplatelet carbon nanofibers such asXGnP® from XG Sciences of Lansing, Mich. The binder 459 may be anysuitable material configured to disperse nanoparticles 458 within binder459 on the surface of carbon fiber fabric 462 and/or to orient carbonfibers of nanoparticles 458 substantially in the axial direction (e.g.,to be axial fibers 104). In some examples, coater 454 and/or a web speedof carbon fiber fabric 462 may be selected to affect a coating thicknessof binder 459 and/or a density of nanoparticles 458 over a surface areaof carbon fiber fabric 462. For example, a slower web speed and/or anincreased coating rate (e.g., volume per time) from coater 454 mayresult in a greater volume and/or density of nanoparticles 458. In someexamples, a web speed and/or coating rate may be selected to result in aselected nanoparticles 458 and/or binder 459 volume and/or densityrelative to a total volume and/or density of composite fiber preform100. For example, a web speed and/or coating rate may be selected toresult in a percent binder 459 volume relative to a total volume ofcomposite fiber preform 100 between about 10% to about 30%. In someexamples, nanoparticles 458 within binder 459 may improve carbon discand/or brake friction performance.

In some examples, combination of carbon fiber fabric 462 and binder 459by coating/depositing and winding onto preform 100 may provideinterlamination strength (e.g., increased peel force) between successivelayers of carbon fiber fabric 462 of brake discs 36, 38 in a format inwhich the orientation of the carbon fibers of carbon fiber fabric 462may be substantially in the axial direction, e.g., axial fibers 104oriented in the thickness direction or “z-direction” of brake discs 36,38 after sectioning of composite fiber preform 100. Axial fibers 104 inthe “z-direction” may have reduced carbon fiber pull-out and an improvedwear rate relative to circumferential fibers 106 and radial fibers 108,and the interlayer adhesion provided by binder 459 may decreasedelamination of layers 102 of brake discs 36, 38.

In some examples, the tension of carbon fiber fabric 462, web speed,and/or an coating rate of coater 454 may be controlled to provide aselected amount of binder 459 and/or nanoparticles 458 in selectedregions of composite fiber preform 100. For example, during winding ofthe inner radial section of preform 100, a first tension of carbon fiberfabric 462, a first web speed, and a first coating rate may provide agreater amount of binder 459 and/or nanoparticles 458 relative to acentral radial section (e.g., central with respect to width W of FIG.3A) wound with a second tension of carbon fiber fabric 462, and/orsecond web speed, and/or second coating rate (e.g., each of which may bevaried independently or in any combination to increase or decrease theamount of binder 459 and/or nanoparticles 458). Similarly, duringwinding of the outer radial section of preform 100, a third tension ofcarbon fiber fabric 462, and/or a third web speed, and/or a thirdcoating rate may provide a greater amount of binder 459 and/ornanoparticles 458 relative to a central radial section. In this way,composite fiber preform 100 may be formed to have a selected amount(e.g., percentage) of binder 459 and/or nanoparticles 458 as a functionof radius of composite fiber preform 100 and brake discs 36, 38.

With reference to both FIGS. 4A and 4B, the in-plane fibers of carbonfiber fabric 412, 462 wound to form composite preform 100 are in theaxial-circumferential plane of brake discs 36, 38 once the discs aresectioned from composite fiber preform 100, e.g., effectivelyre-orienting the carbon fibers of the carbon fiber fabric 412, 462layers 102 as compared with sheet stacking methods. For example and byway of contrast, sheet stacking methods may stack flat sheets of carbonfiber fabric 412, 462 as layers 102 which may then be converted (e.g.,vie die cutting or any other method) to form annular brake discs 36, 38in which the in-plane carbon fibers of each layer of carbon fiber fabric412, 462 are ultimately oriented in the radial-circumferential plane ofbrake discs 36, 38 (e.g., also referred to as the radial-tangentialplane). In other words, the carbon fiber fabric 412, 462 layer stack 102of brake discs 36, 38 according to the techniques disclosed herein is inthe form of concentric annuli having the same axial length, in contrastto sheet stacking methods resulting in an axial layer stack 102 ofcarbon fiber fabric 412, 462 discs having the same radius. As a result,brake discs 36, 38 formed according to the techniques disclosed hereinmay have an increased axial fiber 104 content, an improved wear rate andimproved thermal performance, with interlaminar adhesion and shearresistance being provided at least in part by interlayer 414 and radialfibers 408 in the technique of FIG. 4A and FIG. 7 , and interlayer 464and binder 459 in the technique of FIG. 4B and FIG. 8 . In someexamples, composite preform 100 may comprise brake discs 36, 38, e.g.,without sectioning. In other words, composite preform 100 may be formedas brake discs 36, 38, e.g., with the axial length/thickness desired forforming brake discs 36, 38 as opposed to a preform with a longer axiallength configured to be sectioned to form brake discs 36, 38 with thedesired axial length/thickness.

FIGS. 5A-5C are cross-sectional views of example interlayers 414 withdifferent densities of highly oriented milled carbon fibers, e.g.,radial fibers 408. In the example shown, interlayer 414 includes radialfibers 408. In the examples shown, interlayer 414, e.g., radial fibers408, are disposed on carrier 418 before winding to form composite fiberpreform 100 and removal of carrier 418.

In some examples, the orientation, or orientation distribution, ofradial fibers 408 may be proportional to the density of radial fibers408. For example, FIGS. 5A-5C illustrate three different densities ofradial fibers 408 comprising interlayer 414, with FIG. 5A illustrating alow radial fibers 408 density, FIG. 5B illustrating a medium radialfibers 408 density, and FIG. 5C illustrating a high radial fibers 408density. FIG. 5B illustrates substantially all (approximately 100%) ofradial fibers 408 having their long dimension oriented greater than orequal to 45 degrees from the surface of the carrier 418 (e.g., radialfibers 408 are substantially all oriented within (or equal to) +/−45degrees from the surface normal of the carrier 418). FIG. 5C illustratessubstantially all (e.g., approximately 100%) of radial fibers 408 havingtheir long dimension substantially perpendicular to the surface of thecarrier 418.

FIGS. 6A and 6B are heat maps 500A and 500B of an example rotor brakedisc and adjacent stator brake disc interface. As illustrated in FIG.6A, stator brake disc 502A and adjacent rotor brake disc 504A may definefriction surface interface 506A. Stator brake disc 502A and rotor brakedisc 504A include a non-woven friction composite. During brakingprocedure, friction between stator brake disc 502A and rotor brake disc504A at friction surface interface 506A generates heat. As indicated inheat map 500A, the temperature of friction surface interface 506A isabout 2800° F. In some examples, such temperatures may increase wear ofstator brake disc 502A and rotor brake disc 504A, damage protectivecoatings on stator brake disc 502A and rotor brake disc 504A, and/orreduce the useable life of stator brake disc 502A and rotor brake disc504A.

As illustrated in FIG. 6B, stator brake disc 502B and adjacent rotorbrake disc 504B may define friction surface interface 506B. Stator brakedisc 502B and rotor brake disc 504B material 502B include a frictioncomposite material manufactured using the techniques described herein.As indicated in heat map 500B, during braking procedures, thetemperature of friction surface interface 506B is less 2800° F., such asless than about 2400° F. This reduction in temperature (e.g., relativeto the example of FIG. 6A) may reduce wear of stator brake disc 502B androtor brake disc 504B and/or improve the useable life of protectivecoatings such as antioxidant coatings on stator brake disc 502B androtor brake disc 504B. In this way, brake discs including frictioncomposite materials manufactured using the techniques described hereinmay increase the useable life of the brake discs.

FIG. 7 is a graph 600 of peak antioxidant (AO) temperature versus timefor an example friction composite material manufactured using thetechniques described herein and an example non-woven friction compositematerial. Line 602 illustrates the temperature of the example non-wovenfriction composite material. As illustrated in FIG. 7 , the peaktemperature reaches about 2800° F. during braking procedures. Afterreaching the peak temperature of about 2800° F., the brake cools overtime. Line 604 illustrates the temperature of the example frictioncomposite material manufactured using the techniques described herein.

The friction composite material provides a lower thermal gradient due tothe axial fibers compared to the non-woven friction composite material.For example, as illustrated in FIG. 7 , the peak temperature of thedescribed friction composite material reaches less than about 2400° F.during braking procedures. In some examples, the peak temperature of thedescribed friction composite materials may be about 550° F. less than apeak temperature of the non-woven friction composite material. In someexamples, an antioxidant surface peak temperature of the describedfriction composite materials may be about 350° F. less than a peaktemperature of the non-woven friction composite material. Additionally,the described friction composite materials spend less time above 2000°F. compared to the non-woven friction composite material.

The fiber preforms and carbon-carbon composite brake pads describedherein may be formed using any suitable technique. FIG. 8 is a flowdiagram illustrating an example technique of manufacturing a compositefiber preform and brake pad such as disc brakes 36 and 38 of FIG. 1 .The technique illustrated in FIG. 8 is described with reference tocomposite fiber preform 100 and brake discs 36, 38, fibers 104-108,layers 102, fabric source 402, carbon fiber fabric 412, interlayersource 404, interlayer 414, and radial fibers 408, however, other fiberpreforms or brake discs may be formed using the described techniques andcomposite fiber preform 100 and brake discs 36, 38 may be formed usingother techniques.

An interlayer 414 and a carbon fiber fabric 412 may be combined (700).In some examples, the interlayer 414 and carbon fiber fabric 412 may becombined by virtue of both being wound together around a mandrel and/ora core on a mandrel, e.g., via a roll-to-roll process as illustrated inFIG. 4A to form composite fiber preform 100. In other examples, theinterlayer 414 and carbon fiber fabric 412 may be combined beforewinding about the mandrel, e.g., via pressing, tensioning, and/or anyother suitable technique for combining the interlayer and the carbonfiber fabric.

In some examples, carbon fiber fabric 412 may comprise a materialincluding in-plane carbon fibers, e.g., a carbon felt and/or acarbon-based felt. In some examples, at least 50% of the carbon fibersof carbon fiber fabric 412 are in-plane fibers such as axial fibers 104or circumferential fibers 106, e.g., a portion of carbon fibers of thecarbon fiber fabric 412 having a substantially in-plane orientation isgreater than or equal to about 50%. In some examples, no more than 50%of the carbon fibers of carbon fiber fabric 412 are out-of-plane fiberssuch as radial fibers 108, e.g., a portion of carbon fibers of thecarbon fiber fabric 412 having a substantially out-of-plane orientationis less than or equal to about 50%.

In some examples, interlayer 414 may comprise a plurality of radialfibers 408, e.g., fibers that are “out-of-plane” before being wound,such as a highly oriented milled carbon fiber ply comprising a pluralityof out-of-plane fibers. In some examples, at least 50% of the carbonfibers of interlayer 414 are out-of-plane fibers such as radial fibers108, e.g., a portion of carbon fibers of the interlayer 414 having asubstantially out-of-plane (or radial when wound) orientation is greaterthan or equal to about 50%. In some examples, interlayer 414 maycomprise a carrier 418, such as a peel ply backer, which may beremovable and which may be removed from the highly oriented milledcarbon fiber ply after interlayer 414 and carbon fiber fabric 412 arecombined.

Interlayer 414 and carbon fiber fabric 412 may be combined to introduceone or more of the plurality of out-of-plane fibers of interlayer 414 atleast partially into the carbon fiber fabric 412, e.g., a carbon felt.Interlayer 414 and a carbon fiber fabric 412 may be combined by bringingthe ends of radial fibers 408, e.g., which on the average may comprise a“surface” of interlayer 414, into contact with a surface of carbon fiberfabric 412.

Interlayer 414 and carbon fiber fabric 412 may be wound around a core410 to form a composite fiber preform 100 (702). In some examples,interlayer 414 and carbon fiber fabric 412 may be wound around a mandrelwithout a core 410. In some examples, interlayer 414 and carbon fiberfabric 412 may be wound to form alternating layers of interlayer 414 andcarbon fiber fabric 412, e.g., such as layers 102 of FIG. 3B. In otherexamples, additional carbon fiber fabrics 412 and/or interlayers 414,e.g., from additional fabric sources 402 and/or interlayer sources 404,may be combined in any other suitable layer pattern. For example,interlayer 414 and carbon fiber fabric 412 may be combined with twoadjacent layers of interlayer 414 alternating with one layer of carbonfiber fabric 412, or interlayer 414 and carbon fiber fabric 412 may becombined with one layer of interlayer 414 alternating with two adjacentlayers of carbon fiber fabric 412.

In some examples, winding interlayer 414 and carbon fiber fabric 412onto core 410 or a mandrel may include selecting an outer diameter ofthe core 410 or mandrel to correspond to a selected inner diameter ID ofcomposite fiber preform 100. In some examples, winding interlayer 414and carbon fiber fabric 412 may include controlling a number of windingsto achieve a selected outer diameter OD of composite fiber preform 100.In some examples, core 410 may comprise a filament wound carbon tow, andin some examples composite fiber preform 100 may be removable from core410 or from the mandrel, or core 410 may be removable from the mandrel.

Interlayer 414 and carbon fiber fabric 412 may be consolidated toincrease a fiber volume fraction (FVF) of the composite fiber preform100. For example, interlayer 414 and carbon fiber fabric 412 may beconsolidated by controlling a tension of one or both of the interlayer414 and carbon fiber fabric 412 during combining and/or winding. In someexamples, fabric source 402 and interlayer source 404 may be wound on amandrel, or wound on a core 420 that may be mounted to or on a mandrel.The mandrels may have a braking system, a motor configured to brake, orany other suitable tensioning system. In some examples, a tensioning barmay be used to control a tension of interlayer 414 and/or carbon fiberfabric 412.

In some examples, controlling the tension of at least one of the carbonfiber fabric 412 or the interlayer 414 comprises controlling a percentof a fiber volume relative to a total volume of the fiber preformbetween about 5% to about 35%, or between about 5% to about 25%. Forexample, increasing the tension of at least one of the carbon fiberfabric 412 or the interlayer 414 may stretch or increase the length ofthe carbon fiber fabric 412 or the interlayer 414 in the circumferentialdirection of composite fiber preform 100 while compressing or decreasingthe width/thickness of the carbon fiber fabric 412 or the interlayer 414in the thickness or radial direction of composite fiber preform 100,thereby increasing the density of carbon fiber fabric 412 or interlayer414 of composite fiber preform 100. Composite fiber preform 100 may thenhave an increased amount or volume of carbon fiber content, e.g., eitherfrom carbon fiber fabric 412 or interlayer 414, relative to a fiberpreform in which the tension is not increased. In other words,tensioning of at least one of the carbon fiber fabric 412 or theinterlayer 414 may control the density of the carbon fiber fabric 412 orinterlayer 414 wound about composite fiber preform 100 and consequentlythe density of the carbon fiber content of composite fiber preform 100.

In some examples, a tension of at least one of the carbon fiber fabric412 or the interlayer 414 may be selected to increase or decrease anamount of radial length that at least one radially oriented carbon fiberextends within the carbon fiber fabric 412. In other words, controllingthe tension of at least one of the carbon fiber fabric 412 or theinterlayer 414 may control how much length of the radial fibers 408 ofinterlayer 414 extends into carbon fiber fabric 412. For example,increasing the tension of one of the carbon fiber fabric 412 or theinterlayer 414 increases the radial pressure of that particular layer ofcarbon fiber fabric 412 or the interlayer 414 on the adjacent layer itcomes into contact with during winding, thereby forcing a greater amountof the length of radial fibers 408 of the interlayer 414 to extendwithin the adjacent carbon fiber fabric layer 414.

Generally, controlling the tension of at least one of the carbon fiberfabric 412 or the interlayer 414 may at least partially controlcompression of layers 102 to form a more compacted composite fiberpreform 100, at least partially control an amount of mechanical bindingof layers 102 together via radial fibers 108 to layers 102 together, orboth. In this way, introducing radial fibers 108 via interlayer 414 andcontrolling the mechanical binding via tension control during combiningor winding may control or increase an interlaminar shear strength ofcomposite fiber preform 100 and/or brake discs 36, 38 produced usingcomposite fiber preform 100.

Although not shown, once composite fiber preform 100 has been formed inthe manner described above, the technique may include carbonizing and/orpyrolyzing composite fiber preform 100. Carbonizing and/or pyrolyzingcomposite fiber preform 100 may convert any carbon-precursor materialinto carbon through a thermal degradation process to effectively burnoff any non-carbon material. For example, composite fiber preform 100may be carbonized by heating composite fiber preform 100 in a retortunder inert or reducing conditions to remove the non-carbon constituents(hydrogen, nitrogen, oxygen, etc.) from fibers 104-108. Thecarbonization can be carried out using retort, such as an autoclave, afurnace, a hot isostatic press, a uniaxial hot press, or the like. Ineach of these techniques, composite fiber preform 100 may be heated inthe inert atmosphere at a temperature in the range of, e.g., about 600°C. to about 1000° C. while optionally being mechanically compressed. Themechanical compression may be used to define the geometry (e.g.,thickness (T)) of composite fiber preform 100. In some examples, theretort may be purged with nitrogen for approximately 1 hour, then heatedto about 900° C. over the course of approximately 10 hour toapproximately 20 hours, followed by elevating the temperature to about1050° C. for approximately 1 hour to approximately 2 hours. The retortthen may be held at about 1050° C. for approximately 3 hours toapproximately 6 hours before the carbonized preform is allowed to cool.In some examples, the carbonization step can be carried out at evenhigher temperature, including up to about 1800° C. or up to about 2600°C.

After winding, composite fiber preform 100 may be densified (704). Forexample, composite fiber preform 100 may be subjected to one or moredensification cycles to form a C-C composite. Example densificationcycles may include, for example, being densified by applying one or morecycles of chemical vapor infiltration and/or chemical vapor deposition(CVI/CVD) of a carbonaceous gas. Any suitable carbonaceous gas may beused during the CVI/CVD processing including, for example, carbon-basedgases such as natural gas, methane, ethane, propane, butane, propylene,or acetylene, or a combination thereof. In some examples, theapplication of the carbonaceous gas to densify a composite fiber preform100 via CVI/CVD may occur substantially in a vacuum space (e.g., avessel with an internal environment at less than 100 Torr (e.g., 13.33kPa)) or under an inert gas environment so as to control the chemicaldeposition reaction. In some examples, during application of the CVI/CVDgas, the environment including composite fiber preform 100 may be heatedto an elevated temperature, for example about 900° C. to about 1200° C.,to promote the chemical deposition reaction.

In some examples, axial fibers 104 may increase penetration of thecarbonaceous gas into composite fiber preform 100. For example,composite fiber preform 100 having a greater percentage of axial fibers104 relative to total fibers 104-108 may have better carbonaceous gaspenetration compared to a perform with a relatively lower percentage ofaxial fibers. In some examples, the carbon fibers of carbon fiber fabric412 may be highly dispersed, e.g., as a carbon felt, and may have asubstantially homogeneous porosity structure, which may have improvedcarbonaceous gas penetration and/or infiltration. Better penetration ofthe carbonaceous gas may improve a final density and/or reduce totaltime required for a desired densification.

In other examples, composite fiber preform 100 may be densified usingother suitable techniques including for example, resin infiltration andcarbonization via resin transfer mold (RTM) processing, vacuum pressureinfiltration (VPI) processing, high pressure infiltration (HPI), or thelike. In some examples, the densification step (704) may produce adensified C-C composite substrate having a final density of about 1.60to about 1.95 g/cc, such as about 1.65 to about 1.85 g/cc.

In some examples, composite fiber preform 100 may optionally be wrappedwith a compaction layer around the outer diameter of the composite fiberpreform 100. The compaction layer may be configured to maintain acompaction of the composite fiber preform, and may comprise a filamentwound carbon tow. In some examples, the technique may include thermalcycling composite fiber preform 100 to rigidize at least one of core410, the composite fiber preform 100, or the compaction layer.

In some examples, before or after any one of carbonizing ordensification, composite fiber preform 100 may be sectioned into aplurality of sections having a selected thickness (706). For example,composite fiber preform 100 may be cut using any suitable cutting methodto a plurality of sections that, in some examples, may be subsequentlycarbonized or densified.

In some examples, during or after the densification of composite fiberpreform 100, the major friction surfaces of the resultant C-C compositemay be machined or sculpted into a desired shape, such as a final brakedisc shape. For example, C-C composite substrate may be ground in theshape of a densified C-C composite disc brake having a final thickness T(e.g., about 1.4 inches). Additionally, or alternatively, lug notches 72may be formed at this time.

In some examples, after densification, the technique may includeapplication of one or more coatings to brake discs 36, 38. For example,the technique may include application of an antioxidant coating, such asphosphorus based penetrant systems and/or barrier systems, to brakediscs 36, 38. In some examples, the one or more coatings may improve theperformance of brake discs 36, 38 and/or improve a useable life of brakediscs 36, 38.

FIG. 9 is a flow diagram illustrating another example technique ofmanufacturing a composite fiber preform and disc brake. The techniqueillustrated in FIG. 9 is described with reference to composite fiberpreform 100 and brake discs 36, 38, fibers 104-108, layers 102, fabricsource 452, carbon fiber fabric 462, interlayer source 454, andinterlayer 464, however, other fiber preforms or disc brakes may beformed using the described techniques and composite fiber preform 100and brake discs 36, 38 may be formed using other techniques.

An interlayer 464 may be deposited onto a carbon fiber fabric 462 toform a composite carbon fiber fabric (800). In some examples, interlayer464 may be a binder 459, and an interlayer source such as coater 454 maydeposit the interlayer 464 onto a surface of the carbon fiber fabric454.

In some examples, carbon fiber fabric 452 may comprise a materialincluding in-plane carbon fibers, e.g., a roll of fiber tow fabric, acarbon nonwoven felt, a carbon knit fabric, carbon woven fabric, apolyacrylonitrile (PAN) fiber, an oxidized PAN fiber such as PANOX®, andthe like. In some examples, at least 50% of the carbon fibers of carbonfiber fabric 462 are in-plane fibers such as axial fibers 104 orcircumferential fibers 106, e.g., a portion of carbon fibers of thecarbon fiber fabric 462 having a substantially in-plane orientation isgreater than or equal to about 50%. In some examples, no more than 50%of the carbon fibers of carbon fiber fabric 462 are out-of-plane fiberssuch as radial fibers 108, e.g., a portion of carbon fibers of thecarbon fiber fabric 462 having a substantially out-of-plane orientationis less than or equal to about 50%.

Coater 454 may coat or otherwise deposit interlayer 464 onto a surfaceof carbon fiber fabric 464. Interlayer 464 may comprise a binder 459,and optionally a plurality of nanoparticles 458 mixed within binder 459.In some examples, coater 454 may be a hopper and may deposit the binder459 onto a surface of carbon fiber fabric 462. For example, the binder459 may be a dry powder of binder material, and a hopper may depositand/or sift the dry binder onto carbon fiber fabric 462. The hopper maybe receive and mix nanoparticles 458 with binder 459 and may depositand/or sift the binder 459 with nanoparticles 458 onto the carbon fiberfabric 462. In some examples, coater 454 may deposit or coat a bindersolution onto a surface of carbon fiber fabric 462. For example, a mixerprior to or included with coater 54 may mix the binder 459 with asolvent, such as an organic solvent, methyl ethyl ketone (MEK), acetoneor any suitable solvent, to form a binder solution, and coater 454 maycoat and/or spray a surface of carbon fiber fabric 462 with the bindersolution. A mixer may further mix the binder solution with nanoparticles458 and coater 454 may coat the binder solution with nanoparticles 458onto the carbon fiber fabric 462. In some examples, whether deposited asa dry binder or coated as a binder solution, binder 459 may comprise aweight percent (wt %) of the dry carbon fiber fabric 462 between about20 wt % to about 30 wt %. In some examples, when added to the dry binderor the binder solution, nanoparticles 458 may comprise a weight percent(wt %) of the binder 459 between about 2 wt % to about 10 wt %.

In some examples, nip rollers 466 and/or press roller 468 may compressbinder 459 and carbon fiber fabric 462, e.g., whether binder 459 isdeposited as a dry binder or coated as a binder solution, and whetherbinder 459 contains nanoparticles 458 or not. A system, such as system400, may dry the binder solution, e.g., before or after winding (e.g.,at 802). For example, system 400 may include a dryer, or may include aweb path in binder 459 air dries, e.g., the solvent has time toevaporate.

Interlayer 464 and carbon fiber fabric 462 may be wound around a core410 to form a composite fiber preform 100 (802). In some examples,interlayer 464 and carbon fiber fabric 462 may be wound around a mandrelwithout a core 410. In some examples, interlayer 464 and carbon fiberfabric 462 may be wound to form alternating layers of interlayer 464 andcarbon fiber fabric 462, e.g., such as layers 102 of FIG. 3B.

In some examples, winding interlayer 464 and carbon fiber fabric 462onto core 410 or a mandrel may include selecting an outer diameter ofthe core 410 or mandrel to correspond to a selected inner diameter ID ofcomposite fiber preform 100. In some examples, winding interlayer 464and carbon fiber fabric 462 may include controlling a number of windingsto achieve a selected outer diameter OD of composite fiber preform 100.In some examples, core 410 may comprise a filament wound carbon tow, andin some examples composite fiber preform 100 may be removable from core410 or from the mandrel, or core 410 may be removable from the mandrel.

Interlayer 464 and carbon fiber fabric 462 may be consolidated toincrease a fiber volume fraction (FVF) of the composite fiber preform100. For example, interlayer 464 and carbon fiber fabric 462 may beconsolidated by controlling a tension of carbon fiber fabric 462 duringcombining and/or winding. In some examples, fabric source 452 may bewound on a mandrel, or wound on a core 420 that may be mounted to or ona mandrel. The mandrels may have a braking system, a motor configured tobrake, or any other suitable tensioning system. In some examples, atensioning bar may be used to control a tension of carbon fiber fabric462.

In some examples, controlling the tension of carbon fiber fabric 462comprises controlling a percent of a fiber volume relative to a totalvolume of the fiber preform between about 5% to about 35%, or betweenabout 5% to about 25%. For example, increasing the tension of at leastone of the carbon fiber fabric 462 or the interlayer 464 may stretch orincrease the length of the carbon fiber fabric 462 or the interlayer 464in the circumferential direction of composite fiber preform 100 whilecompressing or decreasing the width/thickness of the carbon fiber fabric462 or the interlayer 464 in the thickness or radial direction ofcomposite fiber preform 100, thereby increasing the density of carbonfiber fabric 462 or interlayer 464 of composite fiber preform 100. Afterdensification, composite fiber preform 100 may then have an increasedamount or volume of carbon fiber content, e.g., either from carbon fiberfabric 462 or interlayer 464, relative to a fiber preform in which thetension is not increased. In other words, tensioning of carbon fiberfabric 462 may control the density of the carbon fiber fabric 462 orinterlayer 464 wound about composite fiber preform 100 and consequentlythe density of the carbon fiber content of composite fiber preform 100.

Generally, controlling the tension of carbon fiber fabric 462 may atleast partially control compression of layers 102 to form a morecompacted composite fiber preform 100, at least partially control anamount of mechanical binding of layers 102 together via binder 459, orboth. In this way, controlling the mechanical binding via tensioncontrol during combining or winding may control or increase aninterlaminar shear strength of composite fiber preform 100 and/or brakediscs 36, 38 produced using composite fiber preform 100.

Although not shown, once composite fiber preform 100 has been formed inthe manner described above, the technique may include curing interlayer464, e.g., curing binder 459, after winding. For example, compositefiber preform 100 may be heated to cure binder 459. In some examples,system 400 may cure binder 459 with or without nanoparticles 458. Insome examples, curing binder 459 may cause binder 459 to increaseadhesion to adjacent layers 102 and increase cohesion of binder 459,thereby increasing an interlaminar shear strength of composite fiberpreform 100 and/or brake discs 36, 38 produced using composite fiberpreform 100.

The technique may further include carbonizing and/or pyrolyzingcomposite fiber preform 100. Carbonizing and/or pyrolyzing compositefiber preform 100 may convert any carbon-precursor material into carbonthrough a thermal degradation process to effectively burn off anynon-carbon material. For example, composite fiber preform 100 may becarbonized by heating composite fiber preform 100 in a retort underinert or reducing conditions to remove the non-carbon constituents(hydrogen, nitrogen, oxygen, etc.) from fibers 104-108. Thecarbonization can be carried out using retort, such as an autoclave, afurnace, a hot isostatic press, a uniaxial hot press, or the like. Ineach of these techniques, composite fiber preform 100 may be heated inthe inert atmosphere at a temperature in the range of, e.g., about 600°C. to about 1000° C. while optionally being mechanically compressed. Themechanical compression may be used to define the geometry (e.g.,thickness (T)) of composite fiber preform 100. In some examples, theretort may be purged with nitrogen for approximately 1 hour, then heatedto about 900° C. over the course of approximately 10 hour toapproximately 20 hours, followed by elevating the temperature to about1050° C. for approximately 1 hour to approximately 2 hours. The retortthen may be held at about 1050° C. for approximately 3 hours toapproximately 6 hours before the carbonized preform is allowed to cool.In some examples, the carbonization step can be carried out at evenhigher temperature, including up to about 1800° C. or up to about 2600°C.

After winding, composite fiber preform 100 may be densified (804). Forexample, composite fiber preform 100 may be subjected to one or moredensification cycles to form a C-C composite. Example densificationcycles may include, for example, being densified by applying one or morecycles of chemical vapor infiltration and/or chemical vapor deposition(CVI/CVD) of a carbonaceous gas. Any suitable carbonaceous gas may beused during the CVI/CVD processing including, for example, carbon-basedgases such as natural gas, methane, ethane, propane, butane, propylene,or acetylene, or a combination thereof. In some examples, theapplication of the carbonaceous gas to densify a composite fiber preform100 via CVI/CVD may occur substantially in a vacuum space (e.g., avessel with an internal environment at less than 100 Torr (e.g., 13.33kPa)) or under an inert gas environment so as to control the chemicaldeposition reaction. In some examples, during application of the CVI/CVDgas, the environment including composite fiber preform 100 may be heatedto an elevated temperature, for example about 900° C. to about 1200° C.,to promote the chemical deposition reaction.

In some examples, axial fibers 104 may increase penetration of thecarbonaceous gas into composite fiber preform 100. For example,composite fiber preform 100 having a greater percentage of axial fibers104 relative to total fibers 104-108 may have better carbonaceous gaspenetration compared to a perform with a relatively lower percentage ofaxial fibers. In some examples, the carbon fibers of carbon fiber fabric412 may be highly dispersed, e.g., as a carbon felt, and may have asubstantially homogeneous porosity structure, which may have improvedcarbonaceous gas penetration and/or infiltration. Better penetration ofthe carbonaceous gas may improve a final density and/or reduce totaltime required for a desired densification.

In other examples, composite fiber preform 100 may be densified usingother suitable techniques including for example, resin infiltration andcarbonization via resin transfer mold (RTM) processing, vacuum pressureinfiltration (VPI) processing, high pressure infiltration (HPI), or thelike. In some examples, the densification step (804) may produce adensified C-C composite substrate having a final density of about 1.60to about 1.95 g/cc, such as about 1.65 to about 1.85 g/cc.

In some examples, composite fiber preform 100 may be wrapped with acompaction layer around the outer diameter of the composite fiberpreform. The compaction layer may be configured to maintain a compactionof the composite fiber preform, and may comprise a filament wound carbontow. In some examples, the technique may include thermal cyclingcomposite fiber preform 100 to rigidize at least one of core 410, thecomposite fiber preform 100, or the compaction layer.

In some examples, before or after any one of carbonizing or partial orcomplete densification, composite fiber preform 100 may be sectionedinto a plurality of sections having a selected thickness (806). Forexample, composite fiber preform 100 may be cut using any suitablecutting method to a plurality of sections that, in some examples, may besubsequently carbonized or densified.

In some examples, during or after the densification of composite fiberpreform 100, the major friction surfaces of the resultant C-C compositemay be sculpted into a desired shape, such as a final brake disc shape.For example, C-C composite substrate may be ground in the shape of adensified C-C composite disc brake having a final thickness T (e.g.,about 1.4 inches). Additionally, or alternatively, lug notches 72 may beformed at this time.

In some examples, after densification, the technique may includeapplication of one or more coatings to disc brake 38. For example, thetechnique may include application of an antioxidant coating, such asphosphorus based penetrant systems and/or barrier systems, to disc brake38. In some examples, the one or more coatings may improve theperformance of disc brake 38 and/or improve a useable life of disc brake38.

The following clauses illustrate example subject matter describedherein.

Clause 1: A method comprising: combining an interlayer and a carbonfiber fabric, wherein the interlayer comprises a highly oriented milledcarbon fiber ply comprising a plurality of out-of-plane carbon fibers;winding the interlayer and the carbon fiber fabric around a core to forma composite fiber preform comprising a plurality of layers defining anannulus extending along a central axis; and densifying the compositefiber preform.

Clause 2: The method of clause 1, wherein the carbon fiber fabriccomprises a plurality of carbon fibers, wherein a portion of theplurality of carbon fibers of the carbon fiber fabric having asubstantially in-plane orientation is greater than or equal to about50%, wherein a portion of the plurality of carbon fibers of the carbonfiber fabric having a substantially out-of-plane orientation is lessthan or equal to about 50%, and wherein the out-of-plane orientation issubstantially parallel with a radial orientation of the composite fiberpreform.

Clause 3: The method of clause 2, wherein the carbon fiber fabriccomprises a carbon felt.

Clause 4: The method of clause 3, wherein combining the interlayer andthe carbon fiber fabric comprises combining the interlayer with thecarbon felt to introduce one or more of the plurality of out-of-planecarbon fibers at least partially into the carbon felt.

Clause 5: The method of any one of clauses 1 through 4, wherein theinterlayer comprises a peel ply backer, the method further comprisingremoving the peel ply backer from the highly oriented milled carbonfiber ply after the interlayer and the carbon fiber fabric are combined.

Clause 6: The method of any one of clauses 1 through 5, furthercomprising consolidating the interlayer and the carbon fiber fabric toincrease a carbon fiber volume fraction of the composite fiber preformvia controlling the tension of at least one of the carbon fiber fabricor the interlayer.

Clause 7: The method of clause 6, wherein controlling the tension of atleast one of the carbon fiber fabric or the interlayer comprisescontrolling the tension such that a percent of a carbon fiber volumerelative to a total volume of the composite fiber preform is betweenabout 5% to about 25%.

Clause 8: The method of clause 7, further comprising selecting a tensionof at least one of the carbon fiber fabric or the interlayer to increaseor decrease an amount of radial length that at least one radiallyoriented carbon fiber extends within the carbon fiber fabric.

Clause 9: The method of any one of clauses 1 through 8, wherein the corecomprises a filament wound carbon tow, wherein the composite fiberpreform is removable from the core.

Clause 10: The method of any one of clauses 1 through 9, furthercomprising wrapping a compaction layer around an outer diameter of thecomposite fiber preform, wherein the compaction layer is configured tomaintain a compaction of the composite fiber preform.

Clause 11: The method of clause 10, where the compaction layer comprisesa filament wound carbon tow.

Clause 12: The method of clause 10 or clause 11, further comprisingthermal cycling the composite fiber preform to rigidize at least one ofthe core, the composite fiber preform, or the compaction layer.

Clause 13: The method of any one of clauses 1 through 12, furthercomprises: carbonizing at least a portion of the composite fiberpreform, wherein densifying the composite fiber preform comprisesdensifying the composite fiber preform via chemical vapor deposition.

Clause 14: The method of any one of clauses 1 through 13, furthercomprising sectioning the at least partially densified composite fiberpreform into one or more discs defining respective composite brake padsor discs.

Clause 15: A composite fiber preform comprises: a carbon fiber fabric;and an interlayer comprising a highly oriented milled carbon fiber plycomprising a plurality of out-of-plane carbon fibers, wherein theinterlayer and the carbon fiber fabric are wound around a core to form acomposite fiber preform comprising a plurality of layers defining anannulus extending along a central axis, wherein the interlayer and thecarbon fiber fabric are at least partially densified.

Clause 16 The composite fiber preform of clause 15, wherein the carbonfiber fabric comprises a plurality of carbon fibers, wherein a portionof the plurality of carbon fibers of the carbon fiber fabric having asubstantially in-plane orientation is greater than or equal to about50%, wherein a portion of the plurality of carbon fibers of the carbonfiber fabric having a substantially out-of-plane orientation is lessthan or equal to about 50%, and wherein the out-of-plane orientation issubstantially parallel with a radial orientation of the composite fiberpreform:

Clause 17: The composite fiber preform of clause 16, wherein the carbonfiber fabric comprises a carbon felt.

Clause 18: The composite fiber preform of clause 17, wherein one or moreof the plurality of out-of-plane carbon fibers of the interlayer are atleast partially introduced into the carbon felt.

Clause 19: The composite fiber preform of any one of clauses 15 through18, further comprising a compaction layer wrapped around an outerdiameter of the composite fiber preform, wherein the compaction layer isconfigured to maintain a compaction of the composite fiber preform.

Clause 20: A system comprising: a fabric source comprising a carbonfiber fabric; an interlayer source comprising an interlayer comprising aplurality of out-of-plane carbon fibers; and a winding apparatusconfigured to wind the carbon fiber fabric and the interlayer around acore to form a composite fiber preform and defining an annulus extendingalong a central longitudinal axis, the composite fiber preformcomprising: a plurality carbon fiber fabric layers extending in an axialdirection parallel with the longitudinal axis and a circumferentialdirection perpendicular to both the radial and axial directions, whereineach of the plurality of carbon fiber fabric layers comprises aplurality of elongate carbon fibers oriented substantially parallel withthe axial and circumferential directions; and a plurality interlayersextending in an axial direction parallel with the longitudinal axis anda circumferential direction perpendicular to both the radial and axialdirections, wherein the plurality of out-of-plane carbon fibers ofinterlayers are oriented substantially parallel with the radialdirection and configured to mechanically bind one or more adjacentcarbon fiber fabric layers.

Clause 21: The system of clause 20, further comprising: a motor coupledto a mandrel coupled to the core, wherein the motor is configured torotate the mandrel; and a controller communicatively coupled to themotor, wherein the controller is configured to control a speed ofrotation of the mandrel.

Clause 22: The system of clause 20 or clause 21, wherein the mandrelcomprises a graphite mandrel.

Clause 23: The system of any one of clauses 20 through 22, wherein themandrel comprises a metal rod and a graphite ring coupled to at least aportion of the metal rod.

Clause 24: The system of any one of clauses 20 through 23, wherein thefabric source comprises a second mandrel, wherein the carbon fiberfabric is wound on the second mandrel.

Clause 25: The system of clause 24, further comprising at least one of atensioner coupled to the second mandrel or a tensioning bar, wherein thetensioner or tensioning bar is configured to, during winding of thecarbon fiber fabric onto the first mandrel, control a tension of thecarbon fiber fabric.

Clause 26: The system of clause 25, wherein the interlayer sourcecomprises a third mandrel, wherein the interlayer is wound on the thirdmandrel.

Clause 27: The system of clause 26, further comprising at least one of atensioner coupled to the third mandrel or a tensioning bar, wherein thetensioner or tensioning bar is configured to, during winding of theinterlayer onto the first mandrel, control a tension of the interlayer.

Clause 28: A method comprising: forming an interlayer on a carbon fiberfabric to form a composite fiber fabric, wherein the interlayercomprises a binder; winding the composite fiber fabric and interlayeraround a core to form a composite fiber preform comprising a pluralityof layers defining an annulus extending along a central axis; anddensifying the composite fiber preform.

Clause 29: The method of clause 28, wherein a portion of carbon fibersof the carbon fiber fabric having a substantially in-plane orientationis greater than or equal to about 50%, wherein a portion of carbonfibers of the carbon fiber fabric having a substantially out-of-planeorientation is less than or equal to about 50%, wherein the out-of-planeorientation is parallel with a radial orientation of the composite fiberpreform.

Clause 30: The method of clause 28 or 29, wherein the binder comprisesat least one of a resin, a thermoset resin, or a phenolic resin.

Clause 31: The method of any one of clauses 28 through 30, whereindepositing the interlayer comprises: depositing the binder in a drypowder form onto the carbon fiber fabric; compressing the binder to thecarbon fiber fabric prior to winding the composite fiber fabric; andcuring, after winding, the binder.

Clause 32: The method of any one of clauses 28 through 31, wherein theinterlayer comprises a plurality of nanoparticles in the binder, themethod further comprising blending the plurality of nanoparticles withthe binder prior to depositing the interlayer.

Clause 33: The method of clause 32, wherein the plurality ofnanoparticles comprise at least one of a carbon nanotube, a carbonnanofiber, or a graphene nanoplatelet.

Clause 34: The method of any one of clauses 28 through 33, whereindepositing the interlayer comprises: mixing the binder with a solvent toform a binder solution; coating a surface of the carbon fiber fabricwith the binder solution; compressing the binder to the carbon fiberfabric prior to winding the composite fiber fabric; drying the bindersolution; and curing, after winding, the binder.

Clause 35: The method of clause 34, further comprising mixing aplurality of nanoparticles with the binder solution prior to coating thebinder.

Clause 36: The method of any one of clauses 28 through 35, furthercomprising consolidating the interlayer and the carbon fiber fabric toincrease a carbon fiber volume fraction of the composite fiber preformvia controlling the tension of the composite carbon fiber fabric.

Clause 37: The method of clause 36, wherein controlling the tension ofthe composite carbon fiber fabric comprises controlling a percent of acarbon fiber volume relative to a total volume of the composite fiberpreform between about 5% to about 35%.

Clause 38: The method of any one of clauses 28 through 37, wherein thecore comprises a filament wound carbon tow, wherein the composite fiberpreform is removable from the core.

Clause 39: The method of any one of clauses 28 through 38, furthercomprising wrapping a compaction layer around an outer diameter of thecomposite fiber preform, wherein the compaction layer is configured tomaintain a compaction of the composite fiber preform, wherein thecompaction layer comprises a filament wound carbon tow.

Clause 40: The method of clause 39, further comprising thermal cyclingthe composite fiber preform to rigidize at least one of the core, thecomposite fiber preform, or the compaction layer.

Clause 41: The method of any one of clauses 28 through 41, furthercomprising: carbonizing at least a portion of the composite fiberpreform, wherein densifying the composite fiber preform comprisesdensifying the composite fiber preform via chemical vapor deposition.

Clause 42: The method of any one of clauses 28 through 42, furthercomprising sectioning the at least partially densified composite fiberpreform into one or more discs defining respective composite brake padsor discs.

Clause 43: A composite fiber preform comprises: a plurality carbon fiberfabric layers wrapped circumferentially about a longitudinal axis andextending in an axial direction parallel with the longitudinal axis,wherein each of the plurality of carbon fiber fabric layers comprises aplurality of elongate carbon fibers; and a plurality interlayers wrappedcircumferentially about the longitudinal axis and extending in the axialdirection, wherein each of the plurality of interlayers are disposedbetween successive layers of the plurality of carbon fabric layers andcomprise a binder configured to mechanically bind one or more adjacentcarbon fiber fabric layers.

Clause 44: The composite fiber preform of clause 43, wherein the bindercomprises at least one of a resin, a thermoset resin, or a phenolicresin.

Clause 45: The composite fiber preform of any of clause 43 or clause 44,wherein the binder comprises a plurality of nanoparticles.

Clause 46: The composite fiber preform of clause 45, wherein theplurality of nanoparticles comprise at least one of a carbon nanotube, acarbon nanofiber, or a graphene nanoplatelet.

Clause 47: A system comprises: a fabric source comprising a carbon fiberfabric; an interlayer source; and a winding apparatus configured to windthe carbon fiber fabric and the interlayer around a core to form acomposite fiber preform and defining an annulus extending along acentral longitudinal axis, the fiber preform comprising: a pluralitycarbon fiber fabric layers extending in an axial direction parallel withthe longitudinal axis and a circumferential direction perpendicular toboth the radial and axial directions, wherein each of the plurality ofcarbon fiber fabric layers comprises a plurality of elongate carbonfibers; and a plurality interlayers extending in an axial directionparallel with the longitudinal axis and a circumferential directionperpendicular to both the radial and axial directions, wherein theinterlayer comprises a binder configured to mechanically bind one ormore adjacent carbon fiber fabric layers.

Clause 48: The system of clause 47, further comprising: a motor coupledto a mandrel coupled to the core, wherein the motor is configured torotate the mandrel; and a controller communicatively coupled to themotor, wherein the controller is configured to control a speed ofrotation of the mandrel.

Clause 49: The system of clause 48, further comprising at least one of atensioner configured to, during winding of the carbon fiber fabric ontothe first mandrel, control a tension of the carbon fiber fabric.

Various examples have been described. These and other examples arewithin the scope of the following claims.

What is claimed is:
 1. A method comprising: combining an interlayer anda carbon fiber fabric, wherein the interlayer comprises a highlyoriented milled carbon fiber ply comprising a plurality of out-of-planecarbon fibers; winding the interlayer and the carbon fiber fabric arounda core to form a composite fiber preform comprising a plurality oflayers defining an annulus extending along a central axis; anddensifying the composite fiber preform.
 2. The method of claim 1,wherein the carbon fiber fabric comprises a plurality of carbon fibers,wherein a portion of the plurality of carbon fibers of the carbon fiberfabric having a substantially in-plane orientation is greater than orequal to about 50%, wherein a portion of the plurality of carbon fibersof the carbon fiber fabric having a substantially out-of-planeorientation is less than or equal to about 50%, and wherein theout-of-plane orientation is substantially parallel with a radialorientation of the composite fiber preform.
 3. The method of claim 2,wherein the carbon fiber fabric comprises a carbon felt.
 4. The methodof claim 3, wherein combining the interlayer and the carbon fiber fabriccomprises combining the interlayer with the carbon felt to introduce oneor more of the plurality of out-of-plane carbon fibers at leastpartially into the carbon felt.
 5. The method of claim 1, wherein theinterlayer comprises a peel ply backer, the method further comprisingremoving the peel ply backer from the highly oriented milled carbonfiber ply after the interlayer and the carbon fiber fabric are combined.6. The method of claim 1, further comprising consolidating theinterlayer and the carbon fiber fabric to increase a carbon fiber volumefraction of the composite fiber preform via controlling the tension ofat least one of the carbon fiber fabric or the interlayer.
 7. The methodof claim 6, wherein controlling the tension of at least one of thecarbon fiber fabric or the interlayer comprises controlling the tensionsuch that a percent of a carbon fiber volume relative to a total volumeof the composite fiber preform is between about 5% to about 25%.
 8. Themethod of claim 7, further comprising selecting a tension of at leastone of the carbon fiber fabric or the interlayer to increase or decreasean amount of radial length that at least one radially oriented carbonfiber extends within the carbon fiber fabric.
 9. The method of claim 1,wherein the core comprises a filament wound carbon tow, wherein thecomposite fiber preform is removable from the core.
 10. The method ofclaim 1, further comprising wrapping a compaction layer around an outerdiameter of the composite fiber preform, wherein the compaction layer isconfigured to maintain a compaction of the composite fiber preform. 11.The method of claim 10, where the compaction layer comprises a filamentwound carbon tow.
 12. The method of claim 10, further comprising thermalcycling the composite fiber preform to rigidize at least one of thecore, the composite fiber preform, or the compaction layer.
 13. Themethod of claim 1, further comprising: carbonizing at least a portion ofthe composite fiber preform, wherein densifying the composite fiberpreform comprises densifying the composite fiber preform via chemicalvapor deposition.
 14. The method of claim 1, further comprisingsectioning the at least partially densified composite fiber preform intoone or more discs defining respective composite brake pads or discs. 15.A composite fiber preform comprising: a carbon fiber fabric; and aninterlayer comprising a highly oriented milled carbon fiber plycomprising a plurality of out-of-plane carbon fibers, wherein theinterlayer and the carbon fiber fabric are wound around a core to form acomposite fiber preform comprising a plurality of layers defining anannulus extending along a central axis, wherein the interlayer and thecarbon fiber fabric are at least partially densified.
 16. The compositefiber preform of claim 15, wherein the carbon fiber fabric comprises aplurality of carbon fibers, wherein a portion of the plurality of carbonfibers of the carbon fiber fabric having a substantially in-planeorientation is greater than or equal to about 50%, wherein a portion ofthe plurality of carbon fibers of the carbon fiber fabric having asubstantially out-of-plane orientation is less than or equal to about50%, and wherein the out-of-plane orientation is substantially parallelwith a radial orientation of the composite fiber preform.
 17. Thecomposite fiber preform of claim 16, wherein the carbon fiber fabriccomprises a carbon felt.
 18. The composite fiber preform of claim 17,wherein one or more of the plurality of out-of-plane carbon fibers ofthe interlayer are at least partially introduced into the carbon felt.19. The composite fiber preform of claim 15, further comprising acompaction layer wrapped around an outer diameter of the composite fiberpreform, wherein the compaction layer is configured to maintain acompaction of the composite fiber preform.
 20. A system comprising: afabric source comprising a carbon fiber fabric; an interlayer sourcecomprising an interlayer comprising a plurality of out-of-plane carbonfibers; and a winding apparatus configured to wind the carbon fiberfabric and the interlayer around a core to form a composite fiberpreform and defining an annulus extending along a central longitudinalaxis, the composite fiber preform comprising: a plurality carbon fiberfabric layers extending in an axial direction parallel with thelongitudinal axis and a circumferential direction perpendicular to boththe radial and axial directions, wherein each of the plurality of carbonfiber fabric layers comprises a plurality of elongate carbon fibersoriented substantially parallel with the axial and circumferentialdirections; and a plurality interlayers extending in an axial directionparallel with the longitudinal axis and a circumferential directionperpendicular to both the radial and axial directions, wherein theplurality of out-of-plane carbon fibers of interlayers are orientedsubstantially parallel with the radial direction and configured tomechanically bind one or more adjacent carbon fiber fabric layers.